Turbine-compressor unit



March 18, 1952 2,589,239

E. FALLON TURBINE-COMPRESSOR UNIT Filed May 16, 1945 6 Sheets-Sheet lFIGJ IO 24 3Q EDUARDO FALLON March 18, 1952 E. FALLON 2,589,239

TURBINE-COMPRESSOR UNIT Filed May 16, 1945 6 Sheets-Sheet 2 gwuwvbwEDUARDO FALLON March 18, 1952 E. FALLON 2,589,239

TURBINE-COMPRESSOR UNIT Filed May 16, 1945 e Sheets-Sheet 4 X XX\XXX X AI06.

gwuwm EDUARDO FALLON March 18, 1952 E. FALLON 2,539,239

TURBINE-COMPRESSOR UNIT Filed May 16, 1945 6 Sheets-Sheet 5 FIG.5

6 EDUARDO FALLON Patented Mar. 18, 1952 Eduardo Fallon, Cartagena,Colombia, assignor, by direct-andmesne assignments, of one-half toMalcolm Mitchell, New York, N. Y., and onehalf .to Carlos Fallon,Washington, .D. 0.

Application May 16, 1945, Serial No.'593,'978

6 Claims.

This invention relates to turbine-compression units such as powerturbines with compressor means delivering to a combustion chamber whichdirectly supplies propulsion gases to the turbine, and such assuper-charges including a turbinedriven by the exhaust of an internalcombustion engine and, in turn, driving a compressor which delivers tothe engine carburetor.

Great 'difficulty'has hitherto been encountered in making such unitsstandup under the high gas temperatures which have to be contended withand ordinarily, to prevent injury to the metal, in the case of'internalcombustion turbines extraneous cooling media have had to be introducedinto the combustion chamber with constant loss of efficiency.

Themain object of the present invention is to overcome theabove-mentioned difficulty. This object is accomplished, essentially, byproviding turbine and compression chambers and a rotor member whichforms a partition between the two chambersthe rotorincluding integrallyconnected turbine and compressor blades which project into therespective chambers, the rotor being made of metalselectedprincipally'for its character of high thermal conductivity; 'By thisconstruction, the combustion chamber heat is rapidly transferred to thecompressor chamber andserves to heat the air being'compressed inthelatter, thus adding greatly to the efiiciency of the compressor.Temperatures throughout the unit are maintained within safe limits withrespect to the materials of which the parts are made.

Theinvention is shown in practical embodi-, ment, b'y'way of example, inthe "accompanying drawings inwhich:

Figure l is a View of apower unit in'accordance'with the inventionpartly in elevation and partly in axial section. I t

Figure 2'is aview of the unit of Figure 1 partly in elevation as seenfrom the left of Figure 1,

witha brokenawaysegment A showing-a section to the flange [2.

as seen from the left of the latter figure, a segment being broken awayand showing a section substantially on line 6-6 of Figure 5.

Referring to Figure 1, the unit comprises a stator including a circularcasing side wall [0 having at its periphery an annular shoulder llterminating'in an annular radial flange l2. Reference numeral 13designates a circular casing side wall parallel to the side wall [0 andshouldered at its outer periphery into a cylindrical peripheral wall l4terminating in an annular radial flange I5 secured in any suitablemanner The inner edge of wall l3 is shouldered into a cylindricalportion 16 which terminates outwardly in an inwardly extendingcompressor'blades which alternate with conc'entric series 28, 29, 30, 3|and 32 of compressor blades on the rotor disc 22. 2 l, disc 22 isprovided with series of openings 33 and between the openings the disc isprovided with a series of fan blades 34 which, when the rotor isrotating in the prescribed direction, serve to draw air in through theopenings 33 and propel it into the compressor "blades.

Between the rotor disc and easing wall I3, the stator includes aparallel annular wall 35 which has a peripheral flange 36 extendingtoward and over the periphery of disc 22 with a running clearance.Projecting outwardly from the inner edge of wall 35 is a cylindrical'wall'3l which is concentrically spaced inwardly of casing wall 16, wall31 terminating outwardly in an inturned annular radial wall 38 spacedfrom wall ll. Ra-

dial'webs 39 join wall 31 with an internal concentric cylindrical wall40 which terminates outwardly in an annular radial flange 4| secured toflange I9 and inwardly in an outwardly flared or belled portion 42 whichterminates adjacent disc 22 with running clearance. The webs 39 may besolid or may be apertured as at 63, Figure 1. They terminate outwardlyin radial edges as at 44 and inwardly beneath the innermost circularseries of turbine blades 45 which project from wall 35towar'd disc 22.Wall 35'is'equipped'with Adjacent the hub a plurality of additionalconcentric series of turbine blades which are alternated with aplurality of concentric series of turbine blades 46 which project fromthe rotor disc. The several circular series of stator blades 23-28 onthe one hand and on the other, project into the space between the wallsand 35 with their ends in alignment, but spaced apart a distance toaccommodate the rotor disc 22..

The combustion chamber defined between walls 31 and 40 is incommunication with the turbine chamber defined between disc 22 and wall35 through a central opening in the latter, the edge of the openingbeing indicated at 41. The combustion chamber has an annular inletopening 48 and outwardly of this opening, and directed between the webs39, devices 49 for fuel and air injection and ignition are secured incircularly arranged openings in wall l1. Projecting from walls35 and 31are a series of radial fins 50 which start at a vertical edge as atFigure 1, and'iterminate in a vertical edge as at 52, these fins havingas one function the positioning of the stator core portion within theouter shell. Wall I0 may be provided with radial fins 53 disposedopposite fins 50. These fins have a lower edge justabove the outerseries of rotary compressor blades 28 and they project from the innersurface of wall ID to. the plane of the joint between flanges l2 and I5.

Flange 36 of wall 35 is spaced substantially inwardly of the peripheralwall l4 and is provided with a multiplicity of radial openings whichregister with radial openings in the peripheral wall},v Referencenumeral 54 designates thimbles inserted through the registering openingsand expanded into tight engagement in the inner openings.

The rotor disc 22 is made of metal characterized by high thermalconductivity, suitable metals being silver, copper, nickel and alloysthereof which may desirably include vanadium to reduce' distortion. Therotor blades may be made integral with the disc and so are in integralconnection. The contemplated integrality can also' be attained bywelding blades of high ther} mal'conductivity to the disc, or theoppositely projecting blades may be portions of the same piece, of metalfixed in apertures in the disc. In any event, the oppositely projectingrotor blades are in direct alignment with each other andjare of the sameradial dimension, for the efiicient-transfer of heat from the combustionchamber to the compressor chamber. The core constituted by the walls 35,31 and 40, the stationary turbine blades, and fins 50, are also made ofa-jmetal of high thermal conductivity.

In starting the apparatus, the rotor is driven in known manner, fuel isinjected and ignited, and the turbine begins to function, exhaustingthrough the thimbles 54. Blades 34 pull air through the central passagedefined by cylindrical wall 40 and the air is compressed and dischargedthrough the spaces between the thimbles and into the annular passagebetween the core and the outer stator shell to the combustion chamber,the path being indicated by the arrows. Some heat is imparted to theincoming air as it traverses the inlet passage defined by wall 43. Asthe air traverses the compression chamber, it abstracts the heat whichhas been transferred from the turbine blades of the rotor to thecompressor blades of the rotor, also from the rotor disc, so that theturbine parts are maintained at a safe temperature. The compressoroutput adsorbs further heat from the fins 50 which are in heatexchanging relation with the wall 35 and stationary turbine blades, andwith the combustion chamber wall 31.

While the exhaust thimbles 54 are shown as discharging into atmosphere,it will be understood that any suitable lead-oif means may be provided,for example, a ring, or volute, manifold. When the thimbles are expandedin the openings in rim 36, they are preferably not seized in theopenings in wall l4, thus permitting relative adjustment of the parts tosome extent as they expand and contract.

In Figures 3 and 4, the arrangement is generally similar to that ofFigures 1 and 2 except that the rotor disc is solid and an air inlet isprovided in the stator at the compressor blade side of the disc,preliminary heating of the air through contact with the combustionchamber being omitted.

Referring to Figures 3 and 4, the stator wall [0a terminates inwardly inan axial opening rimmed by a fiare or bell 6D. The shaft 20a has fixedthereon an elongated inwardly flaring hub 2Ia with which is integral arotor disc 22a. The hub carries a series of fan blades 6| whichsubstantially conform to the annular space between the hub and bell 60and project somewhat outwardly of the latter in abutment with a soliddisc 62 which is fixed to the shaft. The radial wal1 35a terminatesinwardly in an outwardly tapering bell 63 in the combustion chamber 64into which project fuel and air injecting and igniting devices 49. Asshown in Figure 3, a series of injection devices, as at 65, for avaporizable liquid, is provided. For example, water, mercury, etc., maybe injected into the combustion chamber, resulting in an increase in thetotal volume of gases by the vaporization thereof, the vapors commingledwith the products of combustion passing through the power zone of theturbine and producing increased power. Under such conditions the poweroutput of the turbine can be substantially'increased by leading theexhaust to a condenser for the volatilized liquid. The injected liquids,of course, have a cooling efiect in the combustion chamber but this isnot a prime consideration. An appropriate operating temperature in theturbine is maintainable by heat transfer to the air drawn in by theblades BI and passed to the combustion chamber as indicated by thearrows in Figure 3. The rotor, including the disc 22a and the turbineand compressor blades carried thereby, and the blades 6|, are made ofmetal of high thermal conductivity' just as in the first embodiment, andthe same applies to the wall 35a and the fins 50a.

In Figures 5 and 6, the arrangement is like that of Figures 3 and 4except that the unit is constituted as a super-charger. To this end, theside wal1 132) extends straight inwardly into adjacency with shaft 20b.Radial wall 35b has its lower edge flanged and tapered outwardly intoengagement with the inner portion of wall I31) and just outwardly of theflange wal1 I3b is provided with a circular series of openings 10connectable by pipes H with the carburetor of an internal combustionengine in any suitable manner. The hub of the rotor includes a portion12 having running clearance with the inner margin of wall l3b, portionI2 being spaced from the flange of wall 35b and being flared inwardly todefine an annular intake conduit 13. Wall I3!) is provided with a seriesof apertures 14 incommunication with the annular passage 13 and-inconnection with a series of pipes 15 through which the exhaust from theengine can be lead to the turbine. As before, the rotor, wall 35b andfins 502) are made of metal of high thermoconductivity. The showing ofFigure 4 applies also to the super-charger.

By the described system of heat dissipation and utilization, aturbine-compressor unit efficient in operation and long-lived in serviceis provided. Obviously the invention is susceptible of varied embodimentand is not limited as regards specific form and arrangement of partsexcept as in the following claims.

I claim:

1. A turbine-compressor unit comprising a stator having side andperipheral walls defining an annular chamber, a rotor disposed on theaxis of said stator and including a circular disc spaced between saidside walls and having oppositely projecting blades, said rotor beingmade of metal of high thermal conductivity, the blades on one side ofthe disc being constituted as turbine blades and those on the other sideas compressor blades, the stator having an axial air inlet to thecompressor blade side of said disc and the stator including a radialwall of metal of high thermal conductivity between the turbine bladeside of the rotor disc and the adjacent side wall, said radial wallhaving a central inlet for propulsion gases and including an annularflange projecting toward the rotor disc periphery and having a runningclearance therewith, said flange being spaced from said peripheral wall,and spaced apart tubular exhaust members connecting openings in saidflange with openings in said peripheral wall.

2. Apparatus according to claim 1 wherein the turbine and compressorblades are each arranged in concentric series, wherein the side Walladjacent the compression blades has concentric series of bladesalternating with the series of compressor blades and cooperatingtherewith, and wherein said radial wall has concentric series of bladesalternating with the series of compressor blades and cooperatingtherewith.

3. A unit according to claim 1 wherein the stator includes portionsdefining a combustion chamber in communication with the space betweenthe radial wall and adjacent side wall and with said central inlet.

4. A unit according to claim 1 wherein the space between said radialwall and the adjacent side wall and said central inlet are incommunication with separate openings in the stator which extend to theexterior.

5. A unit according to claim 1 wherein the stator includes wallsdefining an annular combustion chamber surrounding the stator axis onthe turbine blade side of said disc in connection with said centralinlet and defining a central air passage, wherein said disc isperforated around its axis so as to place said air passage in connectionwith the compressor blade side of said disc, said passage andperforations constituting the axial air inlet, and wherein the statorincludes walls defining a passage connecting the space between saidradial wall and adjacent side wall with the other end of said combustionchamber.

6. A unit according to claim 1 wherein the stator includes wallsdefining an annular combustion chamber surrounding the stator axis onthe turbine blade side of said disc in connection with said centralinlet and defining a central air passage, wherein said disc isperforated around its axis so as to place said air passage in connectionwith the compressor blade side of said disc, said perforations havingwalls shaped as fan blades adapted to draw air through said air passage,said passage and perforations constituting the axial air inlet, andwherein the stator includes walls defining a passage connecting thespace between said radial wall and adjacent side wall with the outer endof said combustion chamber.

EDUARDO FALLON.

REFERENCES CITED The following references are of record in the file ofthis patent:

UNITED STATES PATENTS Number Name Date 1,057,002 Loftus Mar. 25, 19131,197,755 Moller Sept. 12, 1916 1,256,674 Fdttinger Feb. 19, 19181,868,143 Heinze July 19, 1932 2,256,198 Hahn Sept. 16, 1941 2,256,479Holzwarth Sept. 23, 1941 2,413,225 Grifiith Dec. 24, 1946 2,423,183Forsyth July 1, 1947 2,447,292 Van Acker Aug. 17, 1948 2,471,892 PriceMay 31, 1949 FOREIGN PATENTS Number Country Date 467,630 Great BritainJune 21, 1937 644,159 Germany Apr. 26, 1937 669,249 Germany Dec. 20,1938

